CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.57 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkv-il-1000000-n5.txt Download as CSV file: xf-clarkv-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK V AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0637 0.04225 0.03945 -0.0949 1.0000 0.0073
-15.500 -1.0951 0.03551 0.03249 -0.0999 0.9989 0.0073
-15.250 -1.0949 0.03201 0.02880 -0.1031 0.9962 0.0074
-15.000 -1.0873 0.02974 0.02637 -0.1042 0.9938 0.0076
-14.750 -1.0761 0.02799 0.02447 -0.1043 0.9906 0.0077
-14.500 -1.0589 0.02645 0.02278 -0.1050 0.9885 0.0079
-14.250 -1.0386 0.02510 0.02129 -0.1058 0.9871 0.0081
-14.000 -1.0177 0.02362 0.01968 -0.1067 0.9860 0.0085
-13.750 -0.9948 0.02238 0.01833 -0.1075 0.9850 0.0088
-13.500 -0.9771 0.02142 0.01729 -0.1068 0.9819 0.0092
-13.250 -0.9554 0.02052 0.01629 -0.1068 0.9797 0.0096
-13.000 -0.9317 0.01968 0.01536 -0.1070 0.9779 0.0100
-12.750 -0.9069 0.01892 0.01449 -0.1074 0.9764 0.0104
-12.500 -0.8817 0.01818 0.01366 -0.1077 0.9751 0.0109
-12.250 -0.8581 0.01752 0.01295 -0.1076 0.9732 0.0117
-12.000 -0.8362 0.01698 0.01236 -0.1070 0.9702 0.0124
-11.750 -0.8120 0.01645 0.01177 -0.1068 0.9679 0.0131
-11.500 -0.7868 0.01595 0.01119 -0.1068 0.9658 0.0138
-11.250 -0.7606 0.01551 0.01073 -0.1069 0.9640 0.0148
-11.000 -0.7334 0.01515 0.01035 -0.1071 0.9625 0.0156
-10.750 -0.7093 0.01482 0.00998 -0.1067 0.9598 0.0164
-10.500 -0.6848 0.01447 0.00957 -0.1063 0.9568 0.0171
-10.250 -0.6593 0.01413 0.00916 -0.1061 0.9542 0.0176
-10.000 -0.6334 0.01375 0.00875 -0.1060 0.9518 0.0184
-9.750 -0.6059 0.01350 0.00849 -0.1061 0.9498 0.0192
-9.500 -0.5793 0.01328 0.00824 -0.1060 0.9473 0.0199
-9.250 -0.5541 0.01302 0.00795 -0.1057 0.9440 0.0206
-9.000 -0.5282 0.01274 0.00763 -0.1054 0.9406 0.0212
-8.750 -0.5014 0.01249 0.00731 -0.1054 0.9377 0.0217
-8.500 -0.4737 0.01226 0.00704 -0.1055 0.9351 0.0222
-8.250 -0.4474 0.01202 0.00675 -0.1053 0.9317 0.0225
-8.000 -0.4232 0.01152 0.00620 -0.1048 0.9274 0.0234
-7.750 -0.3967 0.01122 0.00587 -0.1046 0.9234 0.0241
-7.500 -0.3693 0.01096 0.00558 -0.1047 0.9199 0.0247
-7.250 -0.3428 0.01073 0.00532 -0.1045 0.9157 0.0254
-7.000 -0.3163 0.01049 0.00504 -0.1043 0.9109 0.0260
-6.750 -0.2890 0.01025 0.00476 -0.1043 0.9064 0.0266
-6.500 -0.2620 0.01002 0.00448 -0.1042 0.9019 0.0272
-6.250 -0.2352 0.00979 0.00421 -0.1040 0.8964 0.0276
-6.000 -0.2079 0.00957 0.00394 -0.1039 0.8911 0.0279
-5.750 -0.1807 0.00938 0.00371 -0.1038 0.8855 0.0281
-5.500 -0.1538 0.00914 0.00342 -0.1037 0.8793 0.0287
-5.250 -0.1269 0.00889 0.00311 -0.1035 0.8734 0.0295
-5.000 -0.0999 0.00868 0.00287 -0.1034 0.8666 0.0303
-4.750 -0.0725 0.00851 0.00265 -0.1033 0.8602 0.0310
-4.500 -0.0453 0.00835 0.00248 -0.1031 0.8532 0.0319
-4.000 0.0094 0.00810 0.00215 -0.1029 0.8391 0.0337
-3.500 0.0642 0.00790 0.00188 -0.1027 0.8246 0.0358
-3.250 0.0913 0.00779 0.00175 -0.1026 0.8173 0.0398
-3.000 0.1187 0.00768 0.00165 -0.1025 0.8097 0.0443
-2.500 0.1729 0.00747 0.00148 -0.1022 0.7943 0.0665
-2.250 0.1998 0.00739 0.00140 -0.1020 0.7863 0.0767
-2.000 0.2270 0.00731 0.00133 -0.1019 0.7775 0.0865
-1.750 0.2536 0.00724 0.00127 -0.1016 0.7667 0.1034
-1.500 0.2793 0.00714 0.00123 -0.1012 0.7521 0.1334
-1.250 0.3049 0.00709 0.00118 -0.1007 0.7347 0.1597
-1.000 0.3303 0.00700 0.00115 -0.1003 0.7189 0.1970
-0.750 0.3556 0.00683 0.00113 -0.0999 0.7059 0.2614
-0.500 0.3811 0.00670 0.00113 -0.0995 0.6936 0.3226
-0.250 0.4067 0.00660 0.00114 -0.0991 0.6805 0.3733
0.000 0.4326 0.00653 0.00116 -0.0988 0.6675 0.4197
0.250 0.4583 0.00649 0.00118 -0.0984 0.6535 0.4612
0.500 0.4834 0.00650 0.00122 -0.0979 0.6360 0.4992
0.750 0.5077 0.00647 0.00127 -0.0972 0.6158 0.5559
1.000 0.5311 0.00636 0.00135 -0.0964 0.5947 0.6478
1.250 0.5526 0.00620 0.00145 -0.0951 0.5732 0.7631
1.500 0.5747 0.00614 0.00156 -0.0938 0.5536 0.8428
1.750 0.5975 0.00615 0.00167 -0.0925 0.5373 0.9006
2.000 0.6232 0.00625 0.00178 -0.0919 0.5220 0.9436
2.250 0.6545 0.00641 0.00189 -0.0927 0.5048 0.9655
2.500 0.6859 0.00660 0.00199 -0.0936 0.4844 0.9772
2.750 0.7165 0.00683 0.00211 -0.0943 0.4600 0.9858
3.000 0.7474 0.00708 0.00225 -0.0952 0.4343 0.9927
3.500 0.8059 0.00767 0.00256 -0.0963 0.3749 1.0000
3.750 0.8250 0.00798 0.00272 -0.0946 0.3445 1.0000
4.000 0.8458 0.00824 0.00288 -0.0933 0.3220 1.0000
4.250 0.8678 0.00848 0.00304 -0.0922 0.3039 1.0000
4.500 0.8904 0.00870 0.00320 -0.0912 0.2888 1.0000
4.750 0.9128 0.00895 0.00337 -0.0902 0.2708 1.0000
5.000 0.9352 0.00922 0.00356 -0.0892 0.2527 1.0000
5.250 0.9580 0.00948 0.00375 -0.0883 0.2373 1.0000
5.500 0.9809 0.00973 0.00394 -0.0875 0.2231 1.0000
5.750 1.0030 0.01004 0.00417 -0.0865 0.2053 1.0000
6.000 1.0241 0.01041 0.00444 -0.0854 0.1833 1.0000
6.250 1.0459 0.01074 0.00469 -0.0843 0.1678 1.0000
6.500 1.0678 0.01106 0.00495 -0.0834 0.1543 1.0000
6.750 1.0890 0.01142 0.00523 -0.0823 0.1388 1.0000
7.000 1.1094 0.01181 0.00554 -0.0811 0.1221 1.0000
7.250 1.1284 0.01224 0.00587 -0.0795 0.1037 1.0000
7.500 1.1465 0.01271 0.00624 -0.0779 0.0871 1.0000
7.750 1.1656 0.01311 0.00660 -0.0765 0.0763 1.0000
8.000 1.1845 0.01354 0.00699 -0.0750 0.0661 1.0000
8.250 1.2024 0.01403 0.00741 -0.0734 0.0540 1.0000
8.500 1.2188 0.01462 0.00791 -0.0716 0.0404 1.0000
8.750 1.2346 0.01524 0.00846 -0.0697 0.0281 1.0000
9.000 1.2504 0.01588 0.00904 -0.0679 0.0194 1.0000
9.250 1.2675 0.01642 0.00959 -0.0662 0.0157 1.0000
9.500 1.2857 0.01690 0.01008 -0.0648 0.0140 1.0000
9.750 1.3029 0.01743 0.01063 -0.0633 0.0126 1.0000
10.000 1.3198 0.01798 0.01121 -0.0618 0.0115 1.0000
10.250 1.3375 0.01849 0.01175 -0.0604 0.0109 1.0000
10.500 1.3543 0.01905 0.01235 -0.0589 0.0103 1.0000
10.750 1.3702 0.01966 0.01299 -0.0573 0.0097 1.0000
11.000 1.3853 0.02034 0.01370 -0.0557 0.0091 1.0000
11.250 1.3997 0.02106 0.01446 -0.0540 0.0086 1.0000
11.500 1.4152 0.02172 0.01517 -0.0525 0.0082 1.0000
11.750 1.4297 0.02243 0.01593 -0.0510 0.0079 1.0000
12.000 1.4436 0.02321 0.01676 -0.0494 0.0075 1.0000
12.250 1.4568 0.02404 0.01764 -0.0478 0.0072 1.0000
12.500 1.4688 0.02496 0.01860 -0.0461 0.0069 1.0000
12.750 1.4798 0.02598 0.01967 -0.0444 0.0067 1.0000
13.000 1.4888 0.02717 0.02092 -0.0425 0.0064 1.0000
13.250 1.4998 0.02822 0.02204 -0.0410 0.0062 1.0000
13.500 1.5100 0.02935 0.02324 -0.0394 0.0061 1.0000
13.750 1.5194 0.03057 0.02454 -0.0379 0.0060 1.0000
14.000 1.5280 0.03190 0.02594 -0.0365 0.0058 1.0000
14.250 1.5358 0.03330 0.02741 -0.0350 0.0056 1.0000
14.500 1.5428 0.03482 0.02900 -0.0336 0.0055 1.0000
14.750 1.5491 0.03643 0.03068 -0.0323 0.0053 1.0000
15.000 1.5546 0.03818 0.03250 -0.0311 0.0052 1.0000
15.250 1.5591 0.04007 0.03447 -0.0300 0.0051 1.0000
15.500 1.5624 0.04214 0.03661 -0.0290 0.0049 1.0000
15.750 1.5638 0.04450 0.03904 -0.0280 0.0048 1.0000
16.000 1.5630 0.04718 0.04183 -0.0272 0.0047 1.0000
16.250 1.5605 0.05014 0.04490 -0.0266 0.0046 1.0000
16.500 1.5603 0.05294 0.04780 -0.0262 0.0045 1.0000
16.750 1.5592 0.05597 0.05092 -0.0260 0.0045 1.0000
17.000 1.5564 0.05930 0.05436 -0.0261 0.0044 1.0000
17.250 1.5527 0.06284 0.05801 -0.0263 0.0044 1.0000
17.500 1.5469 0.06676 0.06203 -0.0267 0.0043 1.0000
17.750 1.5402 0.07091 0.06630 -0.0274 0.0043 1.0000
18.000 1.5316 0.07547 0.07098 -0.0284 0.0042 1.0000
18.250 1.5216 0.08036 0.07598 -0.0296 0.0042 1.0000
18.500 1.5097 0.08561 0.08136 -0.0311 0.0042 1.0000
18.750 1.4959 0.09130 0.08718 -0.0329 0.0041 1.0000
19.000 1.4809 0.09736 0.09336 -0.0350 0.0041 1.0000
19.250 1.4647 0.10373 0.09986 -0.0374 0.0041 1.0000
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